EP3123020B1 - Method for detecting a failure of a first turbine engine of a twin-engine helicopter and for operating the second turbine engine, and corresponding device - Google Patents

Method for detecting a failure of a first turbine engine of a twin-engine helicopter and for operating the second turbine engine, and corresponding device Download PDF

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Publication number
EP3123020B1
EP3123020B1 EP15717551.4A EP15717551A EP3123020B1 EP 3123020 B1 EP3123020 B1 EP 3123020B1 EP 15717551 A EP15717551 A EP 15717551A EP 3123020 B1 EP3123020 B1 EP 3123020B1
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EP
European Patent Office
Prior art keywords
engine
failure
healthy
engines
inoperative
Prior art date
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Application number
EP15717551.4A
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German (de)
French (fr)
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EP3123020A1 (en
Inventor
Fabien LESCHER
Jean Philippe Jacques MARIN
Philippe Etchepare
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Safran Helicopter Engines SAS
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Safran Helicopter Engines SAS
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Priority to PL15717551T priority Critical patent/PL3123020T3/en
Publication of EP3123020A1 publication Critical patent/EP3123020A1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/12—Plants including a gas turbine driving a compressor or a ducted fan characterised by having more than one gas turbine
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D31/00—Power plant control; Arrangement thereof
    • B64D31/02—Initiating means
    • B64D31/06—Initiating means actuated automatically
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D31/00—Power plant control; Arrangement thereof
    • B64D31/02—Initiating means
    • B64D31/06—Initiating means actuated automatically
    • B64D31/12—Initiating means actuated automatically for equalising or synchronising power plants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/10—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with another turbine driving an output shaft but not driving the compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use
    • F02C6/02—Plural gas-turbine plants having a common power output
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F02C9/46—Emergency fuel control
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/48—Control of fuel supply conjointly with another control of the plant
    • F02C9/56—Control of fuel supply conjointly with another control of the plant with power transmission control
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/329—Application in turbines in gas turbines in helicopters
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/09—Purpose of the control system to cope with emergencies
    • F05D2270/091—Purpose of the control system to cope with emergencies in particular sudden load loss
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/09—Purpose of the control system to cope with emergencies
    • F05D2270/093—Purpose of the control system to cope with emergencies of one engine in a multi-engine system
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/09—Purpose of the control system to cope with emergencies
    • F05D2270/095—Purpose of the control system to cope with emergencies by temporary overriding set control limits
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/335—Output power or torque
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to a method for regulating the turboshaft engines of a twin-engine helicopter.
  • the invention relates to a method for detecting a failure of a first turbine engine, said engine failed, a twin-engine helicopter and control of the second turbine engine, said engine sound.
  • the invention also relates to a twin-rotor helicopter with rotary wing comprising a device for detecting a failure of a first turbine engine and control of a second turbine engine.
  • a twin-engine helicopter is equipped with two turboshaft engines operating at speeds that depend on the flight conditions of the helicopter. It is known that a twin-engine helicopter may have two main regimes, a regime known as AEO ( All Engines Operative ) in which both engines normally operate at predetermined speeds, and a regime known as OEI. ( One Engine Inoperative ) in which one of the turboshaft engines is down. This OEI regime occurs following the loss of an engine. When this event occurs, it is necessary for the valid engine to accelerate rapidly so that it can provide its maximum allowable power in an emergency situation, thereby allowing the helicopter to cope with the perilous situation, and then to be able to continue his flight.
  • AEO All Engines Operative
  • OEI One Engine Inoperative
  • the failed turbine engine will be designated by the words “turboshaft failed” and the valid turbine engine will be designated by the words “turbine engine healthy”.
  • the shorter the duration the safer the flight.
  • the shorter the duration the greater the helicopter's mass at take-off. The minimization of the time that separates the detection of the loss of power from the engine that has failed to obtain the full power of the sound engine therefore has a double interest.
  • the sound engine is controlled to reach its maximum speed in emergency mode, which consists in increasing the maximum limits of torque and speed of the gas turbine up to the maximum permitted stops. Subsequently, the fall in the rotational speed of the rotary wing of the helicopter following the loss of the engine failure will result, via the regulation of the speed of the rotary wing by the healthy engine, an increase in the setpoint fuel flow.
  • the invention aims to provide an effective and economical solution to this technical problem.
  • the invention aims to provide, in at least one embodiment of the invention, a method for detecting a failure of a first turbine engine, according to the steps of claim 1, said engine inoperative, a twin engine helicopter and control of the second turbine engine, said engine sound, which minimizes the time between the detection of the failed engine failure to obtain of the full power of the sound engine.
  • the invention also aims to provide a helicopter according to the features of claim 11.
  • a method according to the invention thus makes it possible to switch the sound engine from a twin-engine configuration to a single-engine configuration as soon as a failure index is detected.
  • This configuration change step is performed by the modification of the motor protection stops in protective stops corresponding to the single engine speed.
  • a subsequent fault confirmation step is then implemented and conditions the control of the immediate increase in fuel flow rate of the sound engine.
  • This failure confirmation step ensures that the helicopter is effectively coping with a real loss of power, which avoids controlling inadvertent acceleration of the healthy engine, which could otherwise cause overspeed of the rotor. If the failure is confirmed, the fuel flow of the healthy engine is immediately increased, which allows to accelerate quickly the healthy engine, without waiting for automatic regulation following the fall of the rotational speed of the rotary wing of the helicopter .
  • a method according to the invention thus makes it possible to quickly detect a failure of an engine and to reach the full power of the sound engine quickly after the detection of the failure.
  • the protections of the sound engine are modified and increased towards the protective stops corresponding to the single-engine speed. If the fault is confirmed, the fuel setpoint is changed.
  • the healthy engine is already in full acceleration, because the increase of the protective stops, the full power in single-engine speed is quickly reached.
  • a method according to the invention has phases of detection of engine failure and sound engine control which are nested one inside the other, which allows to shorten the time between the detection of the failure of said engine broken down and obtaining the full power of said sound engine.
  • each turbine engine comprises a gas generator provided with a combustion chamber, a free turbine supplied with gas by the gas generator, and an output shaft driven in rotation by the free turbine.
  • the protection stops of each motor which define the maximum power speed of this engine, typically correspond to the speed levels of the gas generator, engine torque and / or temperature of the combustion chamber.
  • These protective stops are regulated by a control device known as FADEC for Full Authority Digital Engine Control.
  • FADEC Full Authority Digital Engine Control.
  • the step of modifying the protective stops makes it possible to modify, and in practice to increase, the maximum authorized limits of these various parameters - gas generator speed, engine torque, combustion chamber temperature -. These stops go from their levels corresponding to a twin engine operation at their levels corresponding to a single-engine operation.
  • This step makes it possible to recover measurements of at least one parameter representative of the operating speed of each motor and to detect a difference between these measurements which is greater, in absolute value, than a predetermined threshold.
  • a parameter representative of the operating speed of the motors may be a measured parameter or an estimated parameter. It can for example be the rotational speed of the gas turbine of each engine, or the torque exerted by an output shaft of each turbine engine setting in motion a power transmission, or the temperature of the gases to the inlet of the free turbine of each turbine engine, or the estimation of the quantity of metered flow, etc.
  • each detection of a difference between said measurements is modulated by at least one variable, called modulation variable, representative of normal variations of said measurements during a nominal engine operating speed.
  • each measurement of a difference is modulated by a modulation variable which makes it possible to take into account the normal variations of the measurements during a nominal operating regime. This therefore makes it possible to avoid untimely detections of breakdown due in fact to variations normal measurements.
  • modulation variables thus make it possible to integrate the normal variations of the measurements and thus to reduce the threshold at which a difference must be considered as a failure index.
  • At least one modulation variable is chosen from the following group: type of engine speeds; type of effective balancing of engines; proximity of engine speed and torque measurements of the maximum permissible values for these engines; engine acceleration and deceleration rate; transmission time of said measurements of each parameter representative of the operating speed of the engines.
  • Each of these modulation variables makes it possible to take into account, when determining a difference between the measurements of a parameter representative of the operating speed of the engines, the conditions under which the measurement was made, and thus to modulate the measure of the gap.
  • a method according to the invention also comprises a step of learning nominal deviations between said measurements of at least one parameter representative of the operating speed of the engines, during stabilized speeds of said engines. , said nominal deviations thus determined constituting a modulation variable.
  • Such a learning step makes it possible to create a learning base that provides discrepancies between the measurements of a parameter representative of the operating speed of the engines, which are not representative of a failure of one of the engines. Also, this learning base provides normal deviations under normal operating conditions. In other words, this learning base makes it possible to refine the detection threshold from which a deviation must be considered as a failure index.
  • At least one parameter representative of the operating speed of an engine is a rotational speed of said gas generator or a torque exerted by said output shaft of this engine.
  • the step of detecting a failure index consists in comparing the values of the speeds of the gas turbines and / or the couples exerted by the output trees.
  • the step of modifying the protective stops of said sound motor to protective stops corresponding to a single-engine speed is to increase the torque exerted by said output shaft and to increase the rotational speed of said generator. gas, to reach predetermined nominal values corresponding to a single-engine regime of full power.
  • the step of confirming a failure of said first motor consists in verifying that a plurality of predetermined conditions representative of a real loss of power is verified.
  • the set of predetermined conditions mentioned above makes it possible to confirm the breakdown of said failed engine. In other words, it makes it possible to discriminate a real loss of power on the engine that has failed from another cause that may have led to the detection of a failure index by highlighting a difference greater than a threshold predetermined.
  • said step of controlling an increase in the fuel supply flow rate of said sound engine consists in switching a power anticipation law, connecting a measurement of the collective pitch of the blades of said helicopter to a speed setpoint of said gas generator, in two-engine configuration in anticipation law in single-engine configuration.
  • the increase of the fuel flow in the sound engine consists of switching a power anticipation law in two-engine configuration to an anticipation law in single-engine configuration.
  • a helicopter according to the invention advantageously implements a method according to the invention and a method according to the invention is advantageously implemented by a helicopter according to the invention.
  • module denotes a software element, a subset of a software program that can be compiled separately, either for independent use, or to be assembled with other modules of a program, or a hardware element, or a combination of a hardware element and a software subprogram.
  • a hardware element may include an application-specific integrated circuit (better known by the acronym ASIC for Application-Specific Integrated Circuit ) or a programmable logic circuit or equivalent hardware.
  • ASIC Application-Specific Integrated Circuit
  • a module is an element (software and / or hardware) that ensures a function.
  • the invention also relates to a method for detecting a failure of a first turbine engine of a twin engine helicopter, and control of a second turbine engine, a corresponding device, and a helicopter comprising such a device, characterized in combination by any or some of the features mentioned above or below.
  • the figure 1 illustrates schematically an example of architecture 100 of a twin-engine helicopter adapted to the implementation of a method according to the invention.
  • Each turbine engine 4, 5 comprises respectively and conventionally a generator 41, 51 of gas and a free turbine 42, 52, powered by the generator 41, 51 of gas to provide power.
  • the output of the turbomachines is connected to a transmission transmission box 9.
  • Each generator 41, 51 of gas further comprises a combustion chamber 40, 50 fed with fuel by a fuel distribution circuit not shown in the figure for the sake of clarity.
  • Each turbine engine 4, 5 is coupled to drive means El, E2 and emergency assistance devices U1, U2.
  • Each drive means E1, E2 in rotation of the respective gas generator 41, 51 may be constituted by a starter respectively powered by a starter / generator device equipping the other turbine engine.
  • the drive means E1, E2, the emergency assistance devices U1, U2 and the controls of the turbomachines 4, 5 are managed by a control device 8.
  • This control device is adapted to regulate the protective stops which define the maximum power regime of each engine.
  • the figure 2 is a schematic representation of a method according to an embodiment of the invention.
  • a method according to this embodiment of the invention comprises a step 10 of detecting a failure index of the first turbine engine 4, said engine failure, by measuring a difference greater than a predetermined threshold between values provided by this turboshaft 4 failed and the turbine engine 5 sound, for at least one parameter representative of the operating speed of the engines 4, 5.
  • Blocks 4, 5 of the figure 2 represents respectively the failed turbine engine and the sound turbine engine, including the power and control members.
  • the figure 2 is only intended to present the sequencing of the process steps and the main interactions with the two turboshaft engines.
  • the method further comprises a step 11 of modifying and increasing the protective stops of the sound turbine engine 5 to protective stops corresponding to a single engine speed of full power. This modification of the stops is carried out in the event of a failure index detected in step 10.
  • These protective stops are the rotational speed of the gas generator, the torque on the output shaft and the temperature of the combustion chamber. .
  • the method further comprises a step 12 of confirming the failure of the turbine engine 4 failed by the measurement of a difference greater than a threshold predetermined between the values provided by the turboshaft 4 failed and the turbine engine 5 healthy, for a plurality of parameters representative of the operating speed of the engines.
  • the method comprises a step 13 of controlling an increase in the fuel supply rate of the healthy turbine engine 5 in case of confirmed failure.
  • the step 10 of detecting a failure index consists in recovering, for each engine 4, 5, a measurement of at least one parameter representative of the operating speed of the motors and detecting a difference between said upper measurements, in value absolute, at a predetermined threshold.
  • This parameter is for example the speed of rotation of the generator 41, 51 of gas of each motor or the torque of the output shaft.
  • the measurement of the difference between the values is modulated by at least one modulation variable representative of normal variations of the measurements during a nominal operating regime of the motors 4, 5.
  • This variable 20 is for example representative of the type of speed motors, the type of effective motor balancing, the proximity of the engine speed and torque measurements of the maximum permissible values for those engines, the acceleration and deceleration rate of the engines or the transmission delay of the engines measurements of each parameter representative of the operating speed of the engines.
  • step 10 of detection of an index the difference between the values provided by the motors is calculated and modulated by the modulation variable 20. If a difference greater than a predetermined threshold is detected, then a failure index of the motor 4 is detected.
  • the predetermined threshold from which a deviation is considered sufficiently significant to characterize a failure is 1%. If we consider the motor torque, the predetermined threshold is set at 7%.
  • Step 11 then consists in controlling the full power of the engine 5 of such that it reaches nominal values of single-engine operation, to overcome the failure of the engine 4.
  • this control aims to increase the speed of rotation of the gas turbine and the torque at the output of the turbine engine.
  • Step 12 is to check that the motor 4 is down. To do this, the following tests are performed. It is verified that a signed discrepancy between the rotation speed of the engine generator 41 of the engine 4 failed and the rotation speed of the generator 51 of the engine 5 sound is greater than the difference measured in step 10 of detection of an index when the parameter representative of the operating speed of the engines is the speed of rotation of the gas generators of the engines. It is also verified that the signed discrepancy between the output shaft torque of the failed motor 4 and the output shaft torque of the sound motor 5 is greater than the difference measured during the step of detection of an index when the parameter representative of the operating speed of the motors is the engine torque.
  • the rotational speed of the free turbine 4 of the failed motor 4 is less than a predetermined set value subtracted from a predetermined offset (for example, this offset is set at 0.75% of the speed of rotation).
  • the free turbine and the setpoint is the nominal speed of the free turbine).
  • the time drift of the speed of rotation of the gas generator 51 of the sound engine 5 is greater than a predetermined threshold (for example, the predetermined threshold for the time drift of the sound engine is set at 1% of the speed of the gas generator per second).
  • the time drift of the rotational speed of the gas generator 41 of the engine 4 that has failed is less than a predetermined threshold (for example, the predetermined threshold for the time drift of the engine inoperative is set at 5% of the speed of the gas generator per second).
  • the failure of the engine 4 is confirmed and a drive to the healthy engine is initiated to increase the fuel flow of the healthy engine.
  • this increase in fuel flow is obtained by switching a power anticipation law, connecting a measurement of the collective pitch of the blades of the twin-engine helicopter to a speed setpoint of the gas generator 51, in twin-engine configuration in anticipation law in single-engine configuration.
  • This switching of anticipation laws generates a flow setpoint jump suddenly accelerating the engine 5 healthy, while ensuring the protections of the engine 5 (maximum speed, maximum torque, maximum temperature, no pumping, etc.).
  • this device is housed in the regulating device 8 and this regulating device 8 acts as a detection module, a module for modifying the stops, a fault confirmation module and a control module.
  • the device comprises a computer program product downloadable from a communication network and / or recorded on a computer readable medium and / or executable by a processor, including program code instructions for setting implementation of the method according to the invention, when said program is executed on a computer.
  • This computer program product is for example intended to be executed by the control device 8.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Control Of Turbines (AREA)
  • Control Of Vehicle Engines Or Engines For Specific Uses (AREA)
  • Control Of Eletrric Generators (AREA)
  • Combined Controls Of Internal Combustion Engines (AREA)

Description

1. Domaine technique de l'invention1. Technical field of the invention

L'invention concerne un procédé de régulation des turbomoteurs d'un hélicoptère bimoteur. En particulier, l'invention concerne un procédé de détection d'une défaillance d'un premier turbomoteur, dit moteur en panne, d'un hélicoptère bimoteur et de commande du second turbomoteur, dit moteur sain. L'invention concerne également un hélicoptère bimoteur à voilure tournante comprenant un dispositif de détection d'une défaillance d'un premier turbomoteur et de commande d'un second turbomoteur.The invention relates to a method for regulating the turboshaft engines of a twin-engine helicopter. In particular, the invention relates to a method for detecting a failure of a first turbine engine, said engine failed, a twin-engine helicopter and control of the second turbine engine, said engine sound. The invention also relates to a twin-rotor helicopter with rotary wing comprising a device for detecting a failure of a first turbine engine and control of a second turbine engine.

2. Arrière-plan technologique2. Technological background

L'état de la technique comprend notamment les documents WO-A1-94/10619 et US-A-4 500 966 .The state of the art includes documents WO-A1-94 / 10619 and US-A-4,500,966 .

Un hélicoptère bimoteur est équipé de deux turbomoteurs qui fonctionnent à des régimes qui dépendent des conditions de vol de l'hélicoptère. Il est connu qu'un hélicoptère bimoteur peut présenter deux régimes principaux, un régime connu sous l'acronyme anglais AEO (All Engines Operative) dans lequel les deux turbomoteurs fonctionnent normalement à des régimes prédéterminés, et un régime connu sous l'acronyme anglais OEI (One Engine Inoperative) dans lequel un des turbomoteurs est en panne. Ce régime OEI survient suite à la perte d'un moteur. Lorsque cet événement se produit, il est nécessaire que le moteur valide accélère rapidement pour qu'il puisse fournir sa puissance maximale admissible en situation d'urgence, et permettre ainsi à l'hélicoptère de faire face à la situation périlleuse, puis de pouvoir poursuivre son vol.A twin-engine helicopter is equipped with two turboshaft engines operating at speeds that depend on the flight conditions of the helicopter. It is known that a twin-engine helicopter may have two main regimes, a regime known as AEO ( All Engines Operative ) in which both engines normally operate at predetermined speeds, and a regime known as OEI. ( One Engine Inoperative ) in which one of the turboshaft engines is down. This OEI regime occurs following the loss of an engine. When this event occurs, it is necessary for the valid engine to accelerate rapidly so that it can provide its maximum allowable power in an emergency situation, thereby allowing the helicopter to cope with the perilous situation, and then to be able to continue his flight.

Dans tout le texte qui suit, le turbomoteur défaillant sera désigné par les termes de « turbomoteur en panne » et le turbomoteur valide sera désigné par les termes de « turbomoteur sain ».Throughout the following text, the failed turbine engine will be designated by the words "turboshaft failed" and the valid turbine engine will be designated by the words "turbine engine healthy".

Il se pose donc le problème technique de minimiser la durée qui sépare la détection de la perte de puissance soudaine du turbomoteur en panne et l'obtention de la puissance maximale en régime d'urgence du turbomoteur sain.It therefore raises the technical problem of minimizing the time that separates the detection of the sudden power loss of the failed turbine engine and obtaining the maximum power in emergency mode of the healthy turbine engine.

En effet, plus cette durée est courte et plus le vol est sûr. En outre, plus cette durée est courte et plus l'hélicoptère peut présenter une masse importante au décollage. La minimisation de la durée qui sépare la détection de la perte de puissance du moteur en panne de l'obtention de la pleine puissance du moteur sain présente donc un double intérêt.Indeed, the shorter the duration, the safer the flight. In addition, the shorter the duration, the greater the helicopter's mass at take-off. The minimization of the time that separates the detection of the loss of power from the engine that has failed to obtain the full power of the sound engine therefore has a double interest.

Il est connu aujourd'hui de détecter la perte de puissance du moteur en panne par une comparaison des régimes de fonctionnement des deux turbomoteurs. Si un écart prédéterminé entre les deux régimes de fonctionnement est détecté, le turbomoteur présentant le moins bon régime est déclaré en panne. Cette perte de puissance est détectée par la mise en évidence d'un écart entre les vitesses des turbines à gaz supérieur à un seuil prédéterminé ou d'un écart entre les couples des deux moteurs supérieur à un seuil prédéterminé.It is known today to detect the power loss of the engine failure by a comparison of the operating speeds of the two turboshaft engines. If a predetermined difference between the two operating modes is detected, the turbine engine with the worst speed is declared to be out of order. This loss of power is detected by revealing a difference between the speeds of the gas turbines greater than a predetermined threshold or a difference between the pairs of the two engines greater than a predetermined threshold.

Une fois la perte de puissance détectée, le moteur sain est commandé pour atteindre son régime maximal en régime d'urgence, qui consiste à augmenter les butées maximales de couple et de vitesse de la turbine à gaz jusqu'aux butées maximales autorisées. Par la suite, la chute de la vitesse de rotation de la voilure tournante de l'hélicoptère consécutive à la perte du moteur en panne va entraîner, via la régulation de la vitesse de la voilure tournante par le moteur sain, une augmentation de la consigne de débit de carburant.Once the power loss is detected, the sound engine is controlled to reach its maximum speed in emergency mode, which consists in increasing the maximum limits of torque and speed of the gas turbine up to the maximum permitted stops. Subsequently, the fall in the rotational speed of the rotary wing of the helicopter following the loss of the engine failure will result, via the regulation of the speed of the rotary wing by the healthy engine, an increase in the setpoint fuel flow.

Il se pose le problème technique de fournir une meilleure solution pour minimiser davantage la durée qui sépare la détection de la perte de puissance soudaine du turbomoteur en panne et l'obtention de la puissance maximale en régime d'urgence du turbomoteur sain.There is the technical problem of providing a better solution to further minimize the time between the detection of the sudden power loss of the failed turbine engine and obtaining the maximum power in emergency mode of the healthy turbine engine.

3. Objectifs de l'invention3. Objectives of the invention

L'invention vise à fournir une solution efficace et économique à ce problème technique.The invention aims to provide an effective and economical solution to this technical problem.

En particulier, l'invention vise à fournir, dans au moins un mode de réalisation de l'invention, un procédé de détection d'une défaillance d'un premier turbomoteur, selon les étapes de la revendication 1, dit moteur en panne, d'un hélicoptère bimoteur et de commande du second turbomoteur, dit moteur sain, qui minimise la durée qui sépare la détection de la défaillance du moteur en panne à l'obtention de la pleine puissance du moteur sain.In particular, the invention aims to provide, in at least one embodiment of the invention, a method for detecting a failure of a first turbine engine, according to the steps of claim 1, said engine inoperative, a twin engine helicopter and control of the second turbine engine, said engine sound, which minimizes the time between the detection of the failed engine failure to obtain of the full power of the sound engine.

L'invention vise aussi à fournir un hélicoptère selon les caractéristiques de la revendication 11.The invention also aims to provide a helicopter according to the features of claim 11.

4. Exposé de l'invention4. Presentation of the invention

Pour ce faire, l'invention concerne un procédé de détection d'une défaillance d'un premier turbomoteur, dit moteur en panne, d'un hélicoptère bimoteur à voilure tournante et de commande d'un second turbomoteur, dit moteur sain, chaque moteur comprenant des butées de protection régulées par un dispositif de régulation qui définissent un régime de puissance maximale, caractérisé en ce qu'il comprend :

  • une étape de détection d'un indice de panne dudit moteur en panne,
  • une étape de modification desdites butées de protection dudit moteur sain en des butées de protection correspondant à un régime monomoteur, en cas d'indice de panne détecté,
  • une étape de confirmation d'une panne dudit moteur en panne,
  • une étape de commande d'une d'augmentation immédiate du débit d'alimentation en carburant dudit moteur sain, en cas de panne confirmée, de manière à permettre une accélération du moteur sain sans attendre une régulation automatique du moteur sain suite à une chute de vitesse de ladite voilure tournante résultant de la panne du moteur en panne.
To do this, the invention relates to a method for detecting a failure of a first turbine engine, said engine failed, a twin-rotor helicopter with rotary wing and control of a second turbine engine, said engine sound, each engine comprising protection stops regulated by a regulating device which define a maximum power regime, characterized in that it comprises:
  • a step of detecting a failure index of said engine that has failed,
  • a step of modifying said protective stops of said sound engine into protective stops corresponding to a single-engine speed, in the event of a detected failure index,
  • a step of confirming a failure of said engine failure,
  • a step of controlling an immediate increase in the fuel supply flow rate of said sound engine, in case of confirmed failure, so as to allow an acceleration of the healthy engine without waiting for automatic regulation of the healthy engine following a fall of speed of said rotary wing resulting from engine failure.

Un procédé selon l'invention permet donc de basculer le moteur sain d'une configuration bimoteur vers une configuration monomoteur dès qu'un indice de panne est détecté. Cette étape de changement de configuration est réalisée par la modification des butées de protection du moteur en des butées de protection correspondant au régime monomoteur. Une étape subséquente de confirmation de panne est ensuite mise en oeuvre et conditionne la commande de l'augmentation immédiate du débit d'alimentation en carburant du moteur sain. Cette étape de confirmation de panne permet de garantir que l'hélicoptère fait bien face à une perte réelle de puissance, ce qui évite de commander une accélération intempestive du moteur sain, pouvant sinon provoquer une survitesse du rotor. Si la panne est confirmée, le débit de carburant du moteur sain est immédiatement augmenté, ce qui permet d'accélérer rapidement le moteur sain, sans attendre une régulation automatique suite à la chute de la vitesse de rotation de la voilure tournante de l'hélicoptère.A method according to the invention thus makes it possible to switch the sound engine from a twin-engine configuration to a single-engine configuration as soon as a failure index is detected. This configuration change step is performed by the modification of the motor protection stops in protective stops corresponding to the single engine speed. A subsequent fault confirmation step is then implemented and conditions the control of the immediate increase in fuel flow rate of the sound engine. This failure confirmation step ensures that the helicopter is effectively coping with a real loss of power, which avoids controlling inadvertent acceleration of the healthy engine, which could otherwise cause overspeed of the rotor. If the failure is confirmed, the fuel flow of the healthy engine is immediately increased, which allows to accelerate quickly the healthy engine, without waiting for automatic regulation following the fall of the rotational speed of the rotary wing of the helicopter .

Un procédé selon l'invention permet donc de détecter rapidement une panne d'un moteur et d'atteindre la pleine puissance du moteur sain rapidement après la détection de la panne. Dès qu'un indice de panne est détecté, les protections du moteur sain sont modifiées et augmentées vers les butées de protection correspondant au régime monomoteur. Si la panne est confirmée, la consigne de carburant est modifiée. Le moteur sain étant alors déjà en pleine accélération, du fait de l'augmentation des butées de protection, la pleine puissance en régime monomoteur est rapidement atteinte.A method according to the invention thus makes it possible to quickly detect a failure of an engine and to reach the full power of the sound engine quickly after the detection of the failure. As soon as a fault index is detected, the protections of the sound engine are modified and increased towards the protective stops corresponding to the single-engine speed. If the fault is confirmed, the fuel setpoint is changed. The healthy engine is already in full acceleration, because the increase of the protective stops, the full power in single-engine speed is quickly reached.

Un procédé selon l'invention présente des phases de détection de la panne du moteur en panne et de commande du moteur sain qui sont imbriquées l'une dans l'autre, ce qui permet de raccourcir la durée entre la détection de la défaillance dudit moteur en panne et l'obtention de la pleine puissance dudit moteur sain.A method according to the invention has phases of detection of engine failure and sound engine control which are nested one inside the other, which allows to shorten the time between the detection of the failure of said engine broken down and obtaining the full power of said sound engine.

De manière connue, chaque turbomoteur comprend un générateur de gaz muni d'une chambre de combustion, une turbine libre alimentée en gaz par le générateur de gaz, et un arbre de sortie entraîné en rotation par la turbine libre. Les butées de protection de chaque moteur, qui définissent le régime de puissance maximale de ce moteur, correspondent typiquement à des niveaux de vitesse du générateur de gaz, de couple moteur et/ou de température de la chambre de combustion. Ces butées de protection sont régulées par un dispositif de régulation connu sous l'acronyme anglais FADEC, pour Full Authority Digital Engine Control. L'étape de modification des butées de protection permet de modifier, et en pratique d'augmenter, les limites maximales autorisées de ces différents paramètres - vitesse du générateur de gaz, couple moteur, température de la chambre de combustion -. Ces butées passent de leurs niveaux correspondant à un fonctionnement bimoteur à leurs niveaux correspondant à un fonctionnement monomoteur.In known manner, each turbine engine comprises a gas generator provided with a combustion chamber, a free turbine supplied with gas by the gas generator, and an output shaft driven in rotation by the free turbine. The protection stops of each motor, which define the maximum power speed of this engine, typically correspond to the speed levels of the gas generator, engine torque and / or temperature of the combustion chamber. These protective stops are regulated by a control device known as FADEC for Full Authority Digital Engine Control. The step of modifying the protective stops makes it possible to modify, and in practice to increase, the maximum authorized limits of these various parameters - gas generator speed, engine torque, combustion chamber temperature -. These stops go from their levels corresponding to a twin engine operation at their levels corresponding to a single-engine operation.

Avantageusement et selon l'invention, l'étape de détection d'un indice de panne consiste à :

  • récupérer, pour chaque moteur, au moins une mesure d'au moins un paramètre représentatif du régime de fonctionnement des moteurs,
  • détecter un écart entre lesdites mesures supérieur, en valeur absolue, à un seuil prédéterminé.
Advantageously and according to the invention, the step of detecting a failure index consists of:
  • recovering, for each engine, at least one measurement of at least one parameter representative of the operating speed of the engines,
  • detecting a difference between said measurements greater, in absolute value, at a predetermined threshold.

Cette étape permet de récupérer des mesures d'au moins un paramètre représentatif du régime de fonctionnement de chaque moteur et de détecter un écart entre ces mesures qui est supérieur, en valeur absolue, à un seuil prédéterminé. Un tel paramètre représentatif du régime de fonctionnement des moteurs peut être un paramètre mesuré ou un paramètre estimé. Il peut par exemple s'agir de la vitesse de rotation de la turbine à gaz de chaque moteur, ou du couple exercé par un arbre de sortie de chaque turbomoteur mettant en mouvement une boîte de transmission de puissance, ou de la température des gaz à l'entrée de la turbine libre de chaque turbomoteur, ou de l'estimation de la quantité de débit dosé, etc.This step makes it possible to recover measurements of at least one parameter representative of the operating speed of each motor and to detect a difference between these measurements which is greater, in absolute value, than a predetermined threshold. Such a parameter representative of the operating speed of the motors may be a measured parameter or an estimated parameter. It can for example be the rotational speed of the gas turbine of each engine, or the torque exerted by an output shaft of each turbine engine setting in motion a power transmission, or the temperature of the gases to the inlet of the free turbine of each turbine engine, or the estimation of the quantity of metered flow, etc.

Avantageusement et selon cette variante, chaque détection d'un écart entre lesdites mesures est modulée par au moins une variable, dite variable de modulation, représentative de variations normales desdites mesures lors d'un régime de fonctionnement nominal des moteurs.Advantageously and according to this variant, each detection of a difference between said measurements is modulated by at least one variable, called modulation variable, representative of normal variations of said measurements during a nominal engine operating speed.

Selon cette variante avantageuse, chaque mesure d'un écart est modulée par une variable de modulation qui permet de prendre en compte les variations normales des mesures lors d'un régime de fonctionnement nominal. Cela permet donc d'éviter les détections intempestives de panne due en réalité à des variations normales des mesures. Ces variables de modulation permettent donc d'intégrer les variations normales des mesures et donc de diminuer le seuil à partir duquel un écart doit être considéré comme un indice de panne.According to this advantageous variant, each measurement of a difference is modulated by a modulation variable which makes it possible to take into account the normal variations of the measurements during a nominal operating regime. This therefore makes it possible to avoid untimely detections of breakdown due in fact to variations normal measurements. These modulation variables thus make it possible to integrate the normal variations of the measurements and thus to reduce the threshold at which a difference must be considered as a failure index.

Avantageusement et selon cette variante, au moins une variable de modulation est choisie dans le groupe suivant : type de régimes moteurs ; type d'équilibrage effectif des moteurs ; proximité des mesures des vitesses d'arbre et de couple des moteurs des valeurs maximales autorisées pour ces moteurs ; taux d'accélération et de décélération des moteurs ; délai de transmission desdites mesures de chaque paramètre représentatif du régime de fonctionnement des moteurs.Advantageously and according to this variant, at least one modulation variable is chosen from the following group: type of engine speeds; type of effective balancing of engines; proximity of engine speed and torque measurements of the maximum permissible values for these engines; engine acceleration and deceleration rate; transmission time of said measurements of each parameter representative of the operating speed of the engines.

Chacune de ces variables de modulation permet de prendre en compte, lors de la détermination d'un écart entre les mesures d'un paramètre représentatif du régime de fonctionnement des moteurs, des conditions dans lesquelles la mesure a été effectuée, et donc de moduler la mesure de l'écart.Each of these modulation variables makes it possible to take into account, when determining a difference between the measurements of a parameter representative of the operating speed of the engines, the conditions under which the measurement was made, and thus to modulate the measure of the gap.

Avantageusement, en variante ou en combinaison, un procédé selon l'invention comprend en outre une étape d'apprentissage d'écarts nominaux entre lesdites mesures d'au moins un paramètre représentatif du régime de fonctionnement des moteurs, au cours de régimes stabilisés desdits moteurs, lesdits écarts nominaux ainsi déterminés constituant une variable de modulation.Advantageously, as a variant or in combination, a method according to the invention also comprises a step of learning nominal deviations between said measurements of at least one parameter representative of the operating speed of the engines, during stabilized speeds of said engines. , said nominal deviations thus determined constituting a modulation variable.

Une telle étape d'apprentissage permet de créer une base d'apprentissage qui fournit des écarts entre les mesures d'un paramètre représentatif du régime de fonctionnement des moteurs, qui ne sont pas représentatifs d'une panne d'un des moteurs. Aussi, cette base d'apprentissage fournit des écarts normaux en condition normale de fonctionnement. En d'autres termes, cette base d'apprentissage permet d'affiner le seuil de détection à partir duquel un écart doit être considéré comme un indice de panne.Such a learning step makes it possible to create a learning base that provides discrepancies between the measurements of a parameter representative of the operating speed of the engines, which are not representative of a failure of one of the engines. Also, this learning base provides normal deviations under normal operating conditions. In other words, this learning base makes it possible to refine the detection threshold from which a deviation must be considered as a failure index.

Avantageusement et selon l'invention, au moins un paramètre représentatif du régime de fonctionnement d'un moteur est une vitesse de rotation dudit générateur de gaz ou un couple exercé par ledit arbre de sortie de ce moteur.Advantageously and according to the invention, at least one parameter representative of the operating speed of an engine is a rotational speed of said gas generator or a torque exerted by said output shaft of this engine.

Selon cette variante avantageuse, l'étape de détection d'un indice de panne consiste à comparer les valeurs des vitesses des turbines à gaz et/ou les couples exercés par les arbres de sortie.According to this advantageous variant, the step of detecting a failure index consists in comparing the values of the speeds of the gas turbines and / or the couples exerted by the output trees.

Avantageusement et selon l'invention, l'étape de modification des butées de protection dudit moteur sain vers des butées de protection correspondant à un régime monomoteur consiste à augmenter le couple exercé par ledit arbre de sortie et à augmenter la vitesse de rotation dudit générateur de gaz, pour atteindre des valeurs nominales prédéterminées correspondant à un régime monomoteur de pleine puissance.Advantageously and according to the invention, the step of modifying the protective stops of said sound motor to protective stops corresponding to a single-engine speed is to increase the torque exerted by said output shaft and to increase the rotational speed of said generator. gas, to reach predetermined nominal values corresponding to a single-engine regime of full power.

Avantageusement et selon l'invention, l'étape de confirmation d'une panne dudit premier moteur consiste à vérifier qu'une pluralité de conditions prédéterminées représentatives d'une perte réelle de puissance est vérifiée.Advantageously and according to the invention, the step of confirming a failure of said first motor consists in verifying that a plurality of predetermined conditions representative of a real loss of power is verified.

Avantageusement et selon cette variante, lesdites conditions prédéterminées sont les suivantes :

  • un écart signé entre la vitesse de rotation dudit générateur de gaz dudit moteur en panne et la vitesse de rotation dudit générateur de gaz dudit moteur sain est supérieur à l'écart mesuré dans ladite étape de détection d'un indice pour ce paramètre,
  • un écart signé entre le couple dudit arbre de sortie dudit moteur en panne et le couple dudit arbre de sortie dudit moteur sain est supérieur à l'écart mesuré dans ladite étape de détection d'un indice,
  • une vitesse de rotation de ladite turbine libre dudit moteur en panne est inférieure à une valeur de consigne prédéterminée retranchée d'un offset prédéterminé,
  • une dérive temporelle de la vitesse de rotation dudit générateur à gaz dudit moteur sain est supérieure à un seuil prédéterminé,
  • une dérive temporelle de la vitesse de rotation dudit générateur à gaz dudit moteur en panne est inférieure à un seuil prédéterminé.
Advantageously and according to this variant, said predetermined conditions are as follows:
  • a signed difference between the rotational speed of said gas generator of said failed engine and the rotational speed of said gas generator of said sound engine is greater than the difference measured in said step of detecting an index for this parameter,
  • a signed difference between the torque of said output shaft of said failed motor and the torque of said output shaft of said sound motor is greater than the difference measured in said step of detecting an index,
  • a rotational speed of said free turbine of said failed motor is less than a predetermined reference value subtracted from a predetermined offset,
  • a time drift of the rotational speed of said gas generator of said sound engine is greater than a predetermined threshold,
  • a time drift of the rotational speed of said gas generator of said engine failure is less than a predetermined threshold.

L'ensemble des conditions prédéterminées susmentionnées permet de confirmer la panne dudit moteur en panne. En d'autres termes, il permet de discriminer une perte réelle de puissance sur le moteur en panne d'une autre cause ayant pu conduire à la détection d'un indice de panne par la mise en évidence d'un écart supérieur à un seuil prédéterminé.The set of predetermined conditions mentioned above makes it possible to confirm the breakdown of said failed engine. In other words, it makes it possible to discriminate a real loss of power on the engine that has failed from another cause that may have led to the detection of a failure index by highlighting a difference greater than a threshold predetermined.

Avantageusement et selon l'invention, ladite étape de commande d'une d'augmentation du débit d'alimentation en carburant dudit moteur sain, consiste à commuter une loi d'anticipation de puissance, reliant une mesure du pas collectif des pales dudit hélicoptère à une consigne de vitesse dudit générateur de gaz, en configuration bimoteur en une loi d'anticipation en configuration monomoteur.Advantageously and according to the invention, said step of controlling an increase in the fuel supply flow rate of said sound engine consists in switching a power anticipation law, connecting a measurement of the collective pitch of the blades of said helicopter to a speed setpoint of said gas generator, in two-engine configuration in anticipation law in single-engine configuration.

Selon cette variante, l'augmentation du débit de carburant dans le moteur sain consiste à commuter une loi d'anticipation de puissance en configuration bimoteur à une loi d'anticipation en configuration monomoteur.According to this variant, the increase of the fuel flow in the sound engine consists of switching a power anticipation law in two-engine configuration to an anticipation law in single-engine configuration.

L'invention concerne un hélicoptère bimoteur à voilure tournante comprenant un dispositif de détection d'une défaillance d'un premier turbomoteur, dit moteur en panne, d'un hélicoptère bimoteur et de commande d'un second turbomoteur, chaque moteur comprenant des butées de protection régulées par un dispositif de régulation qui définissent un régime de puissance maximale, dit moteur sain comprenant:

  • un module de détection d'un indice de panne dudit moteur en panne,
  • un module de modification desdites butées de protection dudit moteur sain en des butées de protection correspondant à un régime monomoteur, en cas d'indice de panne détecté,
  • un module de confirmation d'une panne dudit moteur en panne,
  • un module de commande d'une d'augmentation du débit d'alimentation en carburant dudit moteur sain en cas de panne confirmée.
The invention relates to a twin-rotor helicopter with rotary wing comprising a device for detecting a failure of a first turbine engine, said engine inoperative, a twin-engine helicopter and control of a second turbine engine, each engine comprising stops of protection regulated by a regulating device which define a maximum power regime, said sound engine comprising:
  • a module for detecting a failure index of said engine that has failed,
  • a module for modifying said protective stops of said sound engine into protective stops corresponding to a single-engine speed, in the event of a detected failure index,
  • a module for confirming a failure of said engine that has failed,
  • a control module of a fuel supply flow increase of said sound engine in case of confirmed failure.

Un hélicoptère selon l'invention met avantageusement en oeuvre un procédé selon l'invention et un procédé selon l'invention est avantageusement mis en oeuvre par un hélicoptère selon l'invention.A helicopter according to the invention advantageously implements a method according to the invention and a method according to the invention is advantageously implemented by a helicopter according to the invention.

Dans tout le texte, on désigne par module, un élément logiciel, un sous-ensemble d'un programme logiciel, pouvant être compilé séparément, soit pour une utilisation indépendante, soit pour être assemblé avec d'autres modules d'un programme, ou un élément matériel, ou une combinaison d'un élément matériel et d'un sous-programme logiciel. Un tel élément matériel peut comprendre un circuit intégré propre à une application (plus connue sous l'acronyme ASIC pour la dénomination anglaise Application-Specific Integrated Circuit) ou un circuit logique programmable ou tout matériel équivalent. D'une manière générale, un module est donc un élément (logiciel et/ou matériel) qui permet d'assurer une fonction.Throughout the text, the term "module" denotes a software element, a subset of a software program that can be compiled separately, either for independent use, or to be assembled with other modules of a program, or a hardware element, or a combination of a hardware element and a software subprogram. Such a hardware element may include an application-specific integrated circuit (better known by the acronym ASIC for Application-Specific Integrated Circuit ) or a programmable logic circuit or equivalent hardware. In general, a module is an element (software and / or hardware) that ensures a function.

L'invention concerne également un procédé de détection d'une défaillance d'un premier turbomoteur d'un hélicoptère bimoteur, et de commande d'un second turbomoteur, un dispositif correspondant, et un hélicoptère comprenant un tel dispositif, caractérisés en combinaison par tout ou partie des caractéristiques mentionnées ci-dessus ou ci-après.The invention also relates to a method for detecting a failure of a first turbine engine of a twin engine helicopter, and control of a second turbine engine, a corresponding device, and a helicopter comprising such a device, characterized in combination by any or some of the features mentioned above or below.

5. Liste des figures5. List of figures

D'autres buts, caractéristiques et avantages de l'invention apparaîtront à la lecture de la description suivante donnée à titre uniquement non limitatif et qui se réfère aux figures annexées dans lesquelles :

  • la figure 1 est une vue schématique d'une architecture bimoteur pour la mise en oeuvre du procédé selon un mode de réalisation de l'invention,
  • la figure 2 est une vue schématique d'un procédé selon un mode de réalisation de l'invention.
Other objects, features and advantages of the invention will become apparent on reading the following description given solely by way of non-limiting example and which refers to the appended figures in which:
  • the figure 1 is a schematic view of a two-engine architecture for implementing the method according to one embodiment of the invention,
  • the figure 2 is a schematic view of a method according to one embodiment of the invention.

6. Description détaillée d'un mode de réalisation de l'invention6. Detailed description of an embodiment of the invention

La figure 1 illustre schématiquement un exemple d'architecture 100 d'un hélicoptère bimoteur adaptée à la mise en oeuvre d'un procédé selon l'invention. Chaque turbomoteur 4, 5 comporte respectivement et de manière classique un générateur 41, 51 de gaz et une turbine libre 42, 52, alimentée par le générateur 41, 51 de gaz pour fournir de la puissance. La sortie des turbomachines est reliée à une boîte 9 de transmission de puissance. Chaque générateur 41, 51 de gaz comprend en outre une chambre 40, 50 de combustion alimentée en carburant par un circuit de distribution de carburant non représenté sur la figure à des fins de clarté.The figure 1 illustrates schematically an example of architecture 100 of a twin-engine helicopter adapted to the implementation of a method according to the invention. Each turbine engine 4, 5 comprises respectively and conventionally a generator 41, 51 of gas and a free turbine 42, 52, powered by the generator 41, 51 of gas to provide power. The output of the turbomachines is connected to a transmission transmission box 9. Each generator 41, 51 of gas further comprises a combustion chamber 40, 50 fed with fuel by a fuel distribution circuit not shown in the figure for the sake of clarity.

Chaque turbomoteur 4, 5 est couplé à des moyens d'entraînement El, E2 et à des dispositifs d'assistance d'urgence U1, U2.Each turbine engine 4, 5 is coupled to drive means El, E2 and emergency assistance devices U1, U2.

Chaque moyen d'entraînement El, E2 en rotation du générateur de gaz respectif 41, 51 peut être constitué par un démarreur alimenté respectivement par un dispositif démarreur/générateur équipant l'autre turbomachine.Each drive means E1, E2 in rotation of the respective gas generator 41, 51 may be constituted by a starter respectively powered by a starter / generator device equipping the other turbine engine.

Les moyens d'entraînement El, E2, les dispositifs d'assistance d'urgence U1, U2 et les commandes des turbomachines 4, 5 sont gérés par un dispositif 8 de régulation. Ce dispositif de régulation est adapté pour réguler les butées de protection qui définissent le régime de puissance maximale de chaque moteur.The drive means E1, E2, the emergency assistance devices U1, U2 and the controls of the turbomachines 4, 5 are managed by a control device 8. This control device is adapted to regulate the protective stops which define the maximum power regime of each engine.

La figure 2 est une représentation schématique d'un procédé selon un mode de réalisation de l'invention. Un procédé selon ce mode de réalisation de l'invention comprend une étape 10 de détection d'un indice de panne du premier turbomoteur 4, dit moteur en panne, par la mesure d'un écart supérieur à un seuil prédéterminé entre des valeurs fournies par ce turbomoteur 4 en panne et le turbomoteur 5 sain, pour au moins un paramètre représentatif du régime de fonctionnement des moteurs 4, 5.The figure 2 is a schematic representation of a method according to an embodiment of the invention. A method according to this embodiment of the invention comprises a step 10 of detecting a failure index of the first turbine engine 4, said engine failure, by measuring a difference greater than a predetermined threshold between values provided by this turboshaft 4 failed and the turbine engine 5 sound, for at least one parameter representative of the operating speed of the engines 4, 5.

Dans tout le texte, les termes « moteur » et « turbomoteur » sont synonymes et sont donc utilisés pour désigner un dispositif de fourniture de puissance pour un hélicoptère. Les blocs 4, 5 de la figure 2 représente respectivement le turbomoteur en panne et le turbomoteur sain, y compris les organes de puissance et de commande. La figure 2 ne vise qu'à présenter le séquençage des étapes du procédé et les principales interactions avec les deux turbomoteurs.Throughout the text, the terms "engine" and "turbine engine" are synonymous and are therefore used to designate a power supply device for a helicopter. Blocks 4, 5 of the figure 2 represents respectively the failed turbine engine and the sound turbine engine, including the power and control members. The figure 2 is only intended to present the sequencing of the process steps and the main interactions with the two turboshaft engines.

Le procédé comprend en outre une étape 11 de modification et d'augmentation des butées de protection du turbomoteur 5 sain vers des butées de protection correspondant à un régime monomoteur de pleine puissance. Cette modification des butées est effectuée en cas d'indice de panne détecté à l'étape 10. Ces butées de protection sont la vitesse de rotation du générateur de gaz, le couple sur l'arbre de sortie et la température de la chambre de combustion.The method further comprises a step 11 of modifying and increasing the protective stops of the sound turbine engine 5 to protective stops corresponding to a single engine speed of full power. This modification of the stops is carried out in the event of a failure index detected in step 10. These protective stops are the rotational speed of the gas generator, the torque on the output shaft and the temperature of the combustion chamber. .

Le procédé comprend en outre une étape 12 de confirmation de la panne du turbomoteur 4 en panne par la mesure d'un écart supérieur à un seuil prédéterminé entre les valeurs fournies par ce turbomoteur 4 en panne et le turbomoteur 5 sain, pour une pluralité de paramètres représentatifs du régime de fonctionnement des moteurs.The method further comprises a step 12 of confirming the failure of the turbine engine 4 failed by the measurement of a difference greater than a threshold predetermined between the values provided by the turboshaft 4 failed and the turbine engine 5 healthy, for a plurality of parameters representative of the operating speed of the engines.

Enfin le procédé comprend une étape 13 de commande d'une augmentation du débit d'alimentation en carburant du turbomoteur 5 sain en cas de panne confirmée.Finally, the method comprises a step 13 of controlling an increase in the fuel supply rate of the healthy turbine engine 5 in case of confirmed failure.

Chaque étape va maintenant être décrite plus en détail.Each step will now be described in more detail.

L'étape 10 de détection d'un indice de panne consiste à récupérer, pour chaque moteur 4, 5, une mesure d'au moins un paramètre représentatif du régime de fonctionnement des moteurs et de détecter un écart entre lesdites mesures supérieur, en valeur absolue, à un seuil prédéterminé. Ce paramètre est par exemple la vitesse de rotation du générateur 41, 51 de gaz de chaque moteur ou le couple de l'arbre de sortie.The step 10 of detecting a failure index consists in recovering, for each engine 4, 5, a measurement of at least one parameter representative of the operating speed of the motors and detecting a difference between said upper measurements, in value absolute, at a predetermined threshold. This parameter is for example the speed of rotation of the generator 41, 51 of gas of each motor or the torque of the output shaft.

La mesure de l'écart entre les valeurs est modulée par au moins une variable 20 de modulation représentative de variations normales des mesures lors d'un régime de fonctionnement nominal des moteurs 4, 5. Cette variable 20 est par exemple représentative du type de régimes moteurs, du type d'équilibrage effectif des moteurs, de la proximité des mesures des vitesses d'arbre et de couple des moteurs des valeurs maximales autorisées pour ces moteurs, du taux d'accélération et de décélération des moteurs ou du délai de transmission desdites mesures de chaque paramètre représentatif du régime de fonctionnement des moteurs.The measurement of the difference between the values is modulated by at least one modulation variable representative of normal variations of the measurements during a nominal operating regime of the motors 4, 5. This variable 20 is for example representative of the type of speed motors, the type of effective motor balancing, the proximity of the engine speed and torque measurements of the maximum permissible values for those engines, the acceleration and deceleration rate of the engines or the transmission delay of the engines measurements of each parameter representative of the operating speed of the engines.

A l'étape 10 de détection d'un indice, l'écart entre les valeurs fournies par les moteurs est donc calculé, puis modulé par la variable 20 de modulation. Si un écart supérieur à un seuil prédéterminé est décelé, alors un indice de panne du moteur 4 est détecté.In step 10 of detection of an index, the difference between the values provided by the motors is calculated and modulated by the modulation variable 20. If a difference greater than a predetermined threshold is detected, then a failure index of the motor 4 is detected.

Par exemple, si l'on considère la vitesse de rotation du générateur de gaz et selon un mode de réalisation, le seuil prédéterminé à partir duquel un écart est considéré comme suffisamment significatif pour caractériser une panne, est de 1%. Si l'on considère le couple moteur, le seuil prédéterminé est fixé à 7%.For example, if we consider the rotation speed of the gas generator and according to one embodiment, the predetermined threshold from which a deviation is considered sufficiently significant to characterize a failure, is 1%. If we consider the motor torque, the predetermined threshold is set at 7%.

L'étape 11 consiste alors à commander la pleine puissance du moteur 5 de telle sorte qu'il atteigne des valeurs nominales de fonctionnement monomoteur, pour pallier la défaillance du moteur 4. De manière classique, cette commande vise à augmenter la vitesse de rotation de la turbine à gaz et le couple en sortie de turbomoteur.Step 11 then consists in controlling the full power of the engine 5 of such that it reaches nominal values of single-engine operation, to overcome the failure of the engine 4. In a conventional manner, this control aims to increase the speed of rotation of the gas turbine and the torque at the output of the turbine engine.

L'étape 12 consiste à vérifier que le moteur 4 est bien en panne. Pour ce faire, les tests suivants sont effectués. Il est vérifié qu'un écart signé entre la vitesse de rotation du générateur 41 de gaz du moteur 4 en panne et la vitesse de rotation du générateur 51 de gaz du moteur 5 sain est supérieur à l'écart mesuré dans l'étape 10 de détection d'un indice lorsque le paramètre représentatif du régime de fonctionnement des moteurs est la vitesse de rotation des générateurs de gaz des moteurs. Il est aussi vérifié que l'écart signé entre le couple de l'arbre de sortie du moteur 4 en panne et le couple de l'arbre de sortie du moteur 5 sain est supérieur à l'écart mesuré au cours de l'étape de détection d'un indice lorsque le paramètre représentatif du régime de fonctionnement des moteurs est le couple des moteurs. Il est aussi vérifié que la vitesse de rotation de la turbine 42 libre du moteur 4 en panne est inférieure à une valeur de consigne prédéterminée retranchée d'un offset prédéterminé (par exemple, cet offset est fixé à 0,75% de la vitesse de la turbine libre et la valeur de consigne est la vitesse nominale de la turbine libre). Il est aussi vérifié que la dérive temporelle de la vitesse de rotation du générateur 51 de gaz du moteur 5 sain est supérieure à un seuil prédéterminé (par exemple, le seuil prédéterminé pour la dérive temporelle du moteur sain est fixé à 1% de la vitesse du générateur de gaz par seconde). Il est enfin vérifié que la dérive temporelle de la vitesse de rotation du générateur 41 de gaz du moteur 4 en panne est inférieure à un seuil prédéterminé (par exemple, le seuil prédéterminé pour la dérive temporelle du moteur en panne est fixé à 5% de la vitesse du générateur de gaz par seconde).Step 12 is to check that the motor 4 is down. To do this, the following tests are performed. It is verified that a signed discrepancy between the rotation speed of the engine generator 41 of the engine 4 failed and the rotation speed of the generator 51 of the engine 5 sound is greater than the difference measured in step 10 of detection of an index when the parameter representative of the operating speed of the engines is the speed of rotation of the gas generators of the engines. It is also verified that the signed discrepancy between the output shaft torque of the failed motor 4 and the output shaft torque of the sound motor 5 is greater than the difference measured during the step of detection of an index when the parameter representative of the operating speed of the motors is the engine torque. It is also verified that the rotational speed of the free turbine 4 of the failed motor 4 is less than a predetermined set value subtracted from a predetermined offset (for example, this offset is set at 0.75% of the speed of rotation). the free turbine and the setpoint is the nominal speed of the free turbine). It is also verified that the time drift of the speed of rotation of the gas generator 51 of the sound engine 5 is greater than a predetermined threshold (for example, the predetermined threshold for the time drift of the sound engine is set at 1% of the speed of the gas generator per second). Finally, it is verified that the time drift of the rotational speed of the gas generator 41 of the engine 4 that has failed is less than a predetermined threshold (for example, the predetermined threshold for the time drift of the engine inoperative is set at 5% of the speed of the gas generator per second).

Si l'ensemble des conditions susmentionnées est vérifié, la panne du moteur 4 est confirmée et une commande à destination du moteur 5 sain est initiée pour augmenter le débit de carburant du moteur 5 sain.If all of the above conditions are verified, the failure of the engine 4 is confirmed and a drive to the healthy engine is initiated to increase the fuel flow of the healthy engine.

Selon un mode de réalisation de l'invention, cette augmentation du débit de carburant est obtenue par la commutation d'une loi d'anticipation de puissance, reliant une mesure du pas collectif des pales de l'hélicoptère bimoteur à une consigne de vitesse du générateur 51 de gaz, en configuration bimoteur en une loi d'anticipation en configuration monomoteur. Cette commutation de lois d'anticipation engendre un saut de consigne de débit faisant accélérer soudainement le moteur 5 sain, tout en garantissant les protections du moteur 5 (vitesse maximale, couple maximal, température maximale, absence de pompage, etc.).According to one embodiment of the invention, this increase in fuel flow is obtained by switching a power anticipation law, connecting a measurement of the collective pitch of the blades of the twin-engine helicopter to a speed setpoint of the gas generator 51, in twin-engine configuration in anticipation law in single-engine configuration. This switching of anticipation laws generates a flow setpoint jump suddenly accelerating the engine 5 healthy, while ensuring the protections of the engine 5 (maximum speed, maximum torque, maximum temperature, no pumping, etc.).

Un procédé selon l'invention est avantageusement mis en oeuvre par un dispositif de détection d'une défaillance du premier turbomoteur en panne, d'un hélicoptère bimoteur et de commande du second turbomoteur sain comprenant :

  • un module de détection d'un indice de panne dudit moteur en panne,
  • un module de modification desdites butées de protection dudit moteur sain en des butées de protection correspondant à un régime monomoteur, en cas d'indice de panne détecté,
  • un module de confirmation d'une panne dudit moteur en panne,
  • un module de commande d'une d'augmentation du débit d'alimentation en carburant dudit moteur sain en cas de panne confirmée.
A method according to the invention is advantageously implemented by a device for detecting a failure of the first failed turbine engine, a twin-engine helicopter and control of the second healthy turbine engine comprising:
  • a module for detecting a failure index of said engine that has failed,
  • a module for modifying said protective stops of said sound engine into protective stops corresponding to a single-engine speed, in the event of a detected failure index,
  • a module for confirming a failure of said engine that has failed,
  • a control module of a fuel supply flow increase of said sound engine in case of confirmed failure.

Selon un mode de réalisation avantageux, ce dispositif est logé dans le dispositif 8 de régulation et ce dispositif 8 de régulation fait office de module de détection, de module de modification des butées, de module de confirmation de panne et de module de commande.According to an advantageous embodiment, this device is housed in the regulating device 8 and this regulating device 8 acts as a detection module, a module for modifying the stops, a fault confirmation module and a control module.

Selon un mode de réalisation avantageux, le dispositif comprend un produit programme d'ordinateur téléchargeable depuis un réseau de communication et/ou enregistré sur un support lisible par ordinateur et/ou exécutable par un processeur, comprenant des instructions de code de programme pour la mise en oeuvre du procédé selon l'invention, lorsque ledit programme est exécuté sur un ordinateur. Ce produit programme d'ordinateur est par exemple destiné à être exécuté par le dispositif 8 de régulation.According to an advantageous embodiment, the device comprises a computer program product downloadable from a communication network and / or recorded on a computer readable medium and / or executable by a processor, including program code instructions for setting implementation of the method according to the invention, when said program is executed on a computer. This computer program product is for example intended to be executed by the control device 8.

Claims (11)

  1. Method for detecting a malfunction in a first turboshaft engine, referred to as an inoperative engine (4), of a twin-engine helicopter having a rotary wing, and for controlling a second turboshaft engine, referred to as a healthy engine (5), each engine (4, 5) comprising protective stops regulated by a regulation device (8) which define a maximum power regime, characterised in that it comprises:
    - a step (10) of detecting an indication of failure of said inoperative engine (4),
    - a step (11) of modifying said protective stops of said healthy engine (5) into protective stops which correspond to a maximum power single-engine regime, in the case of the detected indication of failure,
    - a step (12) of confirming a failure of said inoperative engine (4),
    - a step (13) of controlling an immediate increase in the flow rate of fuel supply of said healthy engine (5), in the event of a confirmed failure, so as to allow an acceleration of the healthy engine without waiting for an automatic regulation of the healthy engine after a fall in speed of said rotary wing resulting from the failure of the inoperative engine.
  2. Method according to claim 1, characterised in that said step (10) of detecting an indication of failure consists in:
    - retrieving, for each engine, at least one measurement of at least one parameter which is representative of the operating regime of the engines,
    - detecting a difference between said measurements which is greater, in terms of absolute value, than a predetermined threshold.
  3. Method according to claim 2, characterised in that each detection of a difference between said measurements is modulated by at least one variable, referred to as a modulation variable (20), which is representative of normal variations in said measurements during a nominal operating regime of the engines (4, 5).
  4. Method according to claim 3, characterised in that at least one modulation variable (20) is selected from the following group: type of engine regimes (4, 5); type of effective balancing of the engines (4, 5); proximity of the measurements of the shaft and torque speeds of the engines (4, 5) to the maximum permissible values for said engines; acceleration and deceleration rates of the engines (4, 5); period of transmission of said measurements of each parameter which is representative of the operating regime of the engines.
  5. Method according to either claim 3 or claim 4, characterised in that it further comprises a step of learning nominal differences between said measurements of at least one parameter which is representative of the operating regime of the engines (4, 5), during stabilised regimes of said engines, said nominal differences which are determined in this way constituting a modulation variable (20).
  6. Method according to any of claims 2 to 5, wherein each engine comprises a gas generator powering a free turbine which sets into rotation an output shaft, characterised in that at least one parameter which is representative of the operating regime of an engine (4, 5) is a rotational speed of said gas generator or a torque exerted by said output shaft of this engine.
  7. Method according to claim 6, characterised in that said step (11) of modifying the protective stops of said engine (5) into stops corresponding to a single-engine regime consists in increasing the torque exerted by said output shaft and in increasing the rotational speed of said gas generator (51) in order to achieve predetermined rated values corresponding to a maximum power single-engine regime.
  8. Method according to any of claims 1 to 7, characterised in that said step (12) of confirming a failure of said first engine consists in verifying that multiple predetermined conditions which are representative of a real loss of power are verified.
  9. Method according to claims 6 and 8 taken together, characterised in that said predetermined conditions are as follows:
    - a signed difference between the rotational speed of said gas generator (41) of said inoperative engine (4) and the rotational speed of said gas generator (51) of said healthy engine (5) is greater than the difference measured in said step (10) of detecting an index for this parameter,
    - a signed difference between the torque of said output shaft of said inoperative engine (4) and the torque of said output shaft of said healthy engine (5) is greater than the difference measured in said step (10) of detecting an index,
    - a rotational speed of said free turbine (42) of said inoperative engine (4) is less than a predetermined setpoint value which is subtracted from a predetermined offset,
    - a time derivative of the rotational speed of said gas generator (51) of said healthy engine (5) is greater than a predetermined threshold,
    - a time derivative of the rotational speed of said gas generator (41) of said inoperative engine (4) is less than a predetermined threshold.
  10. Method according to claim 9, characterised in that said step (13) of controlling an increase in the flow rate of fuel supply of said healthy engine (5) consists in switching law of anticipation power, which links a measurement of the collective pitch of the blades of said helicopter to a speed setpoint value of said gas generator, in the twin configuration to a law of anticipation in the single-engine configuration.
  11. Twin-engine helicopter having a rotary wing comprising at least a first turboshaft engine, referred to as an inoperative engine(4), and at least a second turboshaft engine, referred to as a healthy engine (5), each engine (4, 5) comprising protective stops regulated by a regulation device which define a maximum power regime, characterized in that it comprises a device for detecting a malfunction in said inoperative engine (4) and controlling said healthy engine (5), said device comprising:
    - a module for detecting an indication of failure of said inoperative engine (4),
    - a module for increasing the protective stops of said healthy engine (5) into stops which correspond to a single-engine regime, in the case of a detected indication of failure,
    - a module for confirming a failure of said inoperative engine (4),
    - a module for controlling an immediate increase in the flow rate of fuel supply of said healthy engine (5), in the event of a confirmed failure, so as to allow an acceleration of the healthy engine (5) without waiting for an automatic regulation of the healthy engine (5) after a fall in speed of said rotary wing resulting from the failure of the inoperative engine (4).
EP15717551.4A 2014-03-27 2015-03-20 Method for detecting a failure of a first turbine engine of a twin-engine helicopter and for operating the second turbine engine, and corresponding device Active EP3123020B1 (en)

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FR1452642A FR3019225B1 (en) 2014-03-27 2014-03-27 METHOD FOR DETECTING FAILURE OF A FIRST TURBOMOTOR OF A BIMOTOR HELICOPTER AND CONTROL OF THE SECOND TURBOMOTOR, AND CORRESPONDING DEVICE
PCT/FR2015/050697 WO2015145041A1 (en) 2014-03-27 2015-03-20 Method for detecting a failure of a first turbine engine of a twin-engine helicopter and for operating the second turbine engine, and corresponding device

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